WO2011054880A2 - Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air - Google Patents
Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air Download PDFInfo
- Publication number
- WO2011054880A2 WO2011054880A2 PCT/EP2010/066753 EP2010066753W WO2011054880A2 WO 2011054880 A2 WO2011054880 A2 WO 2011054880A2 EP 2010066753 W EP2010066753 W EP 2010066753W WO 2011054880 A2 WO2011054880 A2 WO 2011054880A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- annular
- air intake
- air
- bowl
- fins
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to the field of air and fuel injection systems equipping the annular combustion chambers of turbomachines, such as, for example, aircraft turbomachines, and more particularly aircraft turbojets or turboprops.
- turbomachines such as, for example, aircraft turbomachines, and more particularly aircraft turbojets or turboprops.
- injection system the assembly formed by an injector and a mixing device.
- FIG 1 very schematically describes an injection system 10 comprising a fuel injector 12 and a mixing device 14 of a known type fitted to a bottom wall of a combustion chamber (not visible in Figure 1). More specifically, the mixing device 14 comprises, from upstream to downstream in the general direction 16 of the fuel flow in this device 14, a member 18 for centering a head 20 of the injector 12, a air intake ring 22, and an annular wall 24 flared downstream, called "bowl" in what follows.
- the centering member 18 is formed of an annular piece flared upstream, sometimes called “sliding traverse”.
- the air intake ring 22 has fins for printing air passing through this ring a gyration movement about a longitudinal axis 23 of the device 14. For this reason, this ring 22 is commonly called “spin" .
- the bowl 24 is intended to guide the output of the injection system 10 a mixture of air and fuel for igniting in the primary zone of the combustion chamber.
- the mixing device 14 comprises an annular indexing tab 26 engaged between two radial walls 28 integral with the bottom of the combustion chamber to ensure an axial locking of the device 14, while allowing a radial clearance of this device. latest.
- the indexing tab 26 is connected to the bowl 24 by an annular wall 30 extending upstream from a radially outer portion 32 of the bowl 24, which forms a thermal protection collar.
- the aforementioned annular wall 30 comprises a substantially cylindrical portion of revolution 34 connected at its upstream end to the indexing tab 26, and a substantially radial portion 36 whose radially inner end is connected to the bowl 24 and whose radially outer end is connected to the cylindrical portion of revolution 34 above.
- the axial extent of the cylindrical portion 34 of the annular wall 30 determines the axial positioning of the indexing tab 26 relative to the downstream end of the bowl 24, while the radial extent of the radial portion 36 of this wall ring 30 determines the radial positioning of its cylindrical portion 34 relative to an annular baffle 38.
- the radial portion 36 of the aforementioned annular wall 30 further comprises an annular row of orifices 40 for passing a flow of cooling air from the radially outer portion 32 of the bowl 24.
- the bowl 24 has an annular row of orifices 42 for the admission of air into the combustion chamber.
- These air intake ports 42 are supplied with air by an annular cavity 44 which is delimited by the bowl 24, by the annular wall 30 connecting said bowl to the indexing tab 26, and by the downstream side of the crown. admission 22.
- the annular cavity 44 has an annular air inlet opening 46 formed between the air intake ring 22 and the aforementioned annular wall 30.
- the annular opening 46 of the cavity 44 must be sufficiently wide to allow feeding of the air intake orifices 42 of the bowl 24, as well as the feeding of the orifices air intake 40 of the radial portion 36 of the annular wall 30, with a sufficient air flow to allow proper operation of the combustion chamber.
- the invention aims in particular to provide a simple, economical and effective solution to this problem.
- the invention proposes a fuel mixing device for an aircraft turbomachine combustion chamber, comprising, centered on a longitudinal axis of this device, a centering element of a turbomachine injector head, at least an air intake crown comprising fins for the gyration of air about the longitudinal axis, a bowl provided with an annular row of air intake ports, and an annular cavity communicating with the intake ports of the bowl.
- the device comprises channels, formed through the aforementioned fins, for supplying air to the annular cavity communicating with the air intake orifices of the bowl.
- the channels formed through the fins of the air intake ring make it possible to supply air to the annular cavity communicating with the air intake orifices of the bowl, and thus make it possible to avoid the use of an annular opening. as in devices of known type.
- a combination of channels of the type described above with an annular opening remains however possible within the scope of the invention, when this is of interest.
- the invention makes possible the design of mixing devices that are less bulky axially and / or radially.
- the invention allows in particular to bring the head of the injector supported by such device, and the air intake crown of this device, the downstream end of the device, that is to say, the output thereof.
- each of the channels of the fins of the air intake ring is aligned with a corresponding orifice formed in an annular wall delimiting downstream the air intake crown and delimiting in upstream said annular cavity.
- the channels of the fins of the air intake crown open downstream into the annular cavity through the annular wall delimiting downstream the air intake crown.
- This wall extends in general parallel to the radial direction.
- annular wall delimiting downstream the air intake ring advantageously comprises a cylindrical surface mounted on an upstream portion forming sleeve of the bowl.
- the aforementioned annular wall thus makes it possible to secure the assembly formed by the centering element of the injector head and the air intake ring to the bowl.
- the bowl comprises an annular portion located radially outwardly with respect to the air intake orifices of this bowl and connected to an annular support wall of a tongue of radially outwardly projecting indexing for mounting the device in an annular wall of the combustion chamber bottom, the annular support wall aforesaid extending upstream from the bowl and being sealingly connected to the annular wall delimiting downstream the air intake crown.
- annular cavity is closed by the aforementioned annular support wall and by the annular wall delimiting downstream the air intake crown.
- This cavity is thus devoid of annular opening, but can be supplied with air through the channels of the fins of the air intake crown.
- This configuration makes it possible to reduce at best the axial and / or radial extent of the mixing device.
- the aforementioned annular support wall comprises an annular portion of extra thickness in which are provided internal air supply channels opening opposite a thermal protection collar forming the radially outer end of the bowl.
- the aforementioned internal channels make it possible to diffuse on the thermal protection collar a flow of cooling air, which is preferably taken upstream of the device.
- each of the channels of the fins of the air intake ring is aligned with a corresponding orifice formed in an annular wall delimiting upstream the air intake ring and secured to the injector head centering member.
- the channels of the fins of the air intake crown thus pass through this crown air intake from the upstream end to the downstream end thereof.
- the air intake ring is divided into two annular parts by a separating member on both sides of which extend the fins of the air intake ring.
- This characteristic defines in the air intake ring a first annular air passage, opening around the injector head near the latter, and a second air passage annular, extending and opening downstream of the first passage.
- the above-mentioned separating member preferably comprises a radially inner part with an internal profile of convergent-divergent type, intended for the suction, by the venturi effect, of fuel sprayed by the head of an injector supported by the device, this separation member being for this reason sometimes called "venturi".
- the separating member is advantageously made in one piece with the fins of the air intake crown.
- the invention also relates to an annular combustion chamber for a turbomachine, equipped with a plurality of mixing devices of the type described above.
- the invention also relates to a turbomachine, comprising an annular combustion chamber of the type described above.
- FIG. 1 already described, is a partial schematic view in axial section of an injection system for a turbomachine combustion chamber of a known type;
- - Figure 2 is a partial schematic perspective view, with an axial sectional plane, of a mixing device according to a preferred embodiment of the invention, equipping the bottom of a turbomachine combustion chamber;
- FIG. 3 is a schematic perspective view of an air intake ring of the device of Figure 2, shown isolated from this device.
- FIG. 2 illustrates a fuel mixing device 48 mounted in the annular bottom wall 50 of a combustion chamber 52 of an aircraft turbine engine, such as for example an airplane turbojet engine.
- the air intake ring 22 of this device 48 is delimited upstream by a radial annular wall 54 formed at the downstream end of the centering member 18, and downstream by a wall radial ring 56, sometimes called "cup".
- the latter has a cylindrical bearing surface of revolution 58 fixed on an end portion 60 forming a sleeve of the bowl 24.
- the air intake ring 22 is divided into two parts by a separating member 62, shown isolated in FIG.
- the separating member 62 is formed of a wall having a radially outer portion 64 which extends radially and which incorporates the fins 66 of the air intake ring 22, which fins extend from one side to the other. another of said wall.
- the wall forming the separator member 62 further has a radially inner portion 68 with internal profile 69 of convergent-divergent type.
- the separation member 62 defines in the air intake ring 22 a first annular air passage 70, upstream, and a second annular air passage 71, downstream ( Figure 2).
- Each fin 66 of the air intake ring 22 is traversed by a channel 72 which is formed in said fin and which extends substantially in the axial direction, facing a corresponding orifice 74 of the radial annular wall 54 delimiting upstream the air intake ring 22, and facing a corresponding orifice 76 of the radial annular wall 56 delimiting downstream said air intake ring 22.
- the channels 72 of the fins 66 of the air intake ring 22 open downstream into the annular cavity 44 delimited by the bowl 24, by the annular wall 30 supporting the indexing tab 26, and by the radial annular wall 56 defining downstream the air intake ring 22.
- the annular wall 30 supporting the indexing tab 26 is sealingly attached at its upstream end to the radially outer end of the radial annular wall 56 defining downstream the air intake ring 22, so that the annular cavity 22 is closed, and communicates upstream with the outside of the combustion chamber only through the channels 72 formed in the fins 66 of the air intake ring 22.
- annular wall 30 supporting the indexing tab 26 has an annular portion of increased thickness 78 in which are provided internal air supply channels 80 which open at their upstream end outside the mixer device 48, and at their downstream end, opposite the radially outer portion 32 of the bowl 24 which forms a thermal protection collar.
- a fuel injector head (not shown in Figures 2 and 3) is inserted into the centering member 18 and sprays fuel in the form of fine droplets downstream.
- An air flow enters upstream in the device 48 by passing through the first annular passage 70 of the air intake ring 22, whose fins 66 cause the gyration of this air flow.
- the aforementioned air flow then mixes with the fuel from the injector. Part of the fuel is driven downstream by the venturi effect by flowing along the internal profile 69 of the separating member 62, and is sprayed at the downstream end of this inner profile 69.
- Another flow of air enters the device downstream passing through the second annular passage 71 of the air intake ring 22, whose fins 66 also cause the gyration of this flow of air.
- the aforementioned air flow is then guided downstream by the internal part 68 of the separation member 62.
- air enters the channels 72 formed in the fins 66 to feed the annular cavity 44 and the combustion chamber 52 via the air intake orifices 42 of the bowl 24.
- a flow of air also flows from upstream to downstream in the channels 80 of the annular wall 30 supporting the indexing tab 26.
- This air flow makes it possible to ventilate and cool the radially outer portion 32 of the bowl 24, which protects the device from thermal radiation coming from inside the combustion chamber 52.
- the device 48 has a reduced axial size due to a coming together of the air intake ring 22 and the annular wall 30 supporting the indexing tab 26 and integral with the bowl 24, made possible by the invention.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB201207621A GB2487332B (en) | 2009-11-05 | 2010-11-03 | Fuel mixing device for turbine engine combustion chamber comprising improved air feed means |
US13/503,737 US9097425B2 (en) | 2009-11-05 | 2010-11-03 | Fuel mixing device for turbine engine combustion chamber comprising improved air feed means |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0957839A FR2952166B1 (fr) | 2009-11-05 | 2009-11-05 | Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air |
FR0957839 | 2009-11-05 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2011054880A2 true WO2011054880A2 (fr) | 2011-05-12 |
WO2011054880A3 WO2011054880A3 (fr) | 2011-10-20 |
Family
ID=42014965
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2010/066753 WO2011054880A2 (fr) | 2009-11-05 | 2010-11-03 | Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air |
Country Status (4)
Country | Link |
---|---|
US (1) | US9097425B2 (fr) |
FR (1) | FR2952166B1 (fr) |
GB (1) | GB2487332B (fr) |
WO (1) | WO2011054880A2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104114950A (zh) * | 2012-02-15 | 2014-10-22 | 斯奈克玛 | 用于涡轮机组燃烧室的空气和燃料喷射装置 |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BR112013028196B1 (pt) * | 2011-05-17 | 2021-06-22 | Snecma | Câmara anular de combustão para uma turbomáquina e turbomáquina |
FR2975466B1 (fr) * | 2011-05-17 | 2013-05-24 | Snecma | Chambre annulaire de combustion pour une turbomachine |
FR2988813B1 (fr) * | 2012-03-29 | 2017-09-01 | Snecma | Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
JP5924618B2 (ja) * | 2012-06-07 | 2016-05-25 | 川崎重工業株式会社 | 燃料噴射装置 |
FR3003632B1 (fr) | 2013-03-19 | 2016-10-14 | Snecma | Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent |
GB2543803B (en) * | 2015-10-29 | 2019-10-30 | Rolls Royce Plc | A combustion chamber assembly |
US10801726B2 (en) * | 2017-09-21 | 2020-10-13 | General Electric Company | Combustor mixer purge cooling structure |
US10808934B2 (en) | 2018-01-09 | 2020-10-20 | General Electric Company | Jet swirl air blast fuel injector for gas turbine engine |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3570242A (en) * | 1970-04-20 | 1971-03-16 | United Aircraft Corp | Fuel premixing for smokeless jet engine main burner |
FR2572463B1 (fr) * | 1984-10-30 | 1989-01-20 | Snecma | Systeme d'injection a geometrie variable. |
FR2596102B1 (fr) * | 1986-03-20 | 1988-05-27 | Snecma | Dispositif d'injection a vrille axialo-centripete |
FR2752917B1 (fr) * | 1996-09-05 | 1998-10-02 | Snecma | Systeme d'injection a degre d'homogeneisation avancee |
US6389815B1 (en) * | 2000-09-08 | 2002-05-21 | General Electric Company | Fuel nozzle assembly for reduced exhaust emissions |
FR2903172B1 (fr) * | 2006-06-29 | 2008-10-17 | Snecma Sa | Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette |
FR2903171B1 (fr) * | 2006-06-29 | 2008-10-17 | Snecma Sa | Agencement a liaison par crabot pour chambre de combustion de turbomachine |
FR2908867B1 (fr) | 2006-11-16 | 2012-06-15 | Snecma | Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif |
FR2925146B1 (fr) * | 2007-12-14 | 2009-12-25 | Snecma | Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
US8281597B2 (en) * | 2008-12-31 | 2012-10-09 | General Electric Company | Cooled flameholder swirl cup |
FR2941288B1 (fr) * | 2009-01-16 | 2011-02-18 | Snecma | Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine |
-
2009
- 2009-11-05 FR FR0957839A patent/FR2952166B1/fr active Active
-
2010
- 2010-11-03 WO PCT/EP2010/066753 patent/WO2011054880A2/fr active Application Filing
- 2010-11-03 US US13/503,737 patent/US9097425B2/en active Active
- 2010-11-03 GB GB201207621A patent/GB2487332B/en active Active
Non-Patent Citations (1)
Title |
---|
None |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104114950A (zh) * | 2012-02-15 | 2014-10-22 | 斯奈克玛 | 用于涡轮机组燃烧室的空气和燃料喷射装置 |
Also Published As
Publication number | Publication date |
---|---|
US20120204567A1 (en) | 2012-08-16 |
FR2952166B1 (fr) | 2012-01-06 |
GB2487332B (en) | 2013-08-28 |
FR2952166A1 (fr) | 2011-05-06 |
GB2487332A (en) | 2012-07-18 |
WO2011054880A3 (fr) | 2011-10-20 |
GB201207621D0 (en) | 2012-06-13 |
US9097425B2 (en) | 2015-08-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2011054880A2 (fr) | Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air | |
EP1806536B1 (fr) | Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboréacteur | |
EP2539638B1 (fr) | Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection d'air ameliorant le melange air-carburant | |
CA2646959C (fr) | Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine | |
EP2616742B1 (fr) | Carénage aérodynamique pour fond de chambre de combustion de turbomachine | |
FR2941288A1 (fr) | Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine | |
CA2754419C (fr) | Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air | |
EP2815183A2 (fr) | Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine | |
WO2013060985A1 (fr) | Module de chambre de combustion de turbomachine d'aéronef et procédé de conception de celui-ci | |
EP3039342B1 (fr) | Chambre de combustion pour turbomachine a admission d'air homogène au travers de systèmes d'injection de carburant | |
EP3784958B1 (fr) | Système d'injection pour une chambre annulaire de combustion de turbomachine | |
FR2952703A1 (fr) | Guide d'une bougie d'allumage dans une chambre de combustion d'une turbomachine | |
FR2958015A1 (fr) | Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant entre deux flux d'air coaxiaux | |
FR2958373A1 (fr) | Chambre de combustion dans une turbomachine | |
FR2948749A1 (fr) | Systeme d'injection de carburant pour une chambre de combustion de turbomachine | |
FR3055950B1 (fr) | Chambre de combustion pour turbomachine comprenant des moyens pour ameliorer le refroidissement d'une paroi annulaire dans le sillage d'un obstacle | |
FR2965604A1 (fr) | Chambre de combustion de turbomachine | |
FR2957659A1 (fr) | Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant en sortie d'une double vrille d'admission d'air | |
EP3969813B1 (fr) | Chambre de combustion comprenant des moyens de refroidissement d'une zone d'enveloppe annulaire en aval d'une cheminée | |
FR2952700A1 (fr) | Guidage d'une bougie dans une chambre de combustion de turbomachine | |
FR3022597A1 (fr) | Diffuseur a triple flux pour module de turbomachine comprenant des dispositifs de canalisation d'air entre les deux parois de separation du diffuseur | |
FR2952702A1 (fr) | Guidage d'une bougie d'allumage dans une chambre de combustion | |
FR2979005A1 (fr) | Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees | |
FR2943762A1 (fr) | Systeme d'injection de carburant dans une chambre de combustion de turbomachine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 10774207 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13503737 Country of ref document: US |
|
ENP | Entry into the national phase |
Ref document number: 1207621 Country of ref document: GB Kind code of ref document: A Free format text: PCT FILING DATE = 20101103 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 1207621.2 Country of ref document: GB |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 10774207 Country of ref document: EP Kind code of ref document: A2 |